CN106460274A - A method of producing a continuous fibre reinforcement layer from individual fibre mats - Google Patents
A method of producing a continuous fibre reinforcement layer from individual fibre mats Download PDFInfo
- Publication number
- CN106460274A CN106460274A CN201480079936.6A CN201480079936A CN106460274A CN 106460274 A CN106460274 A CN 106460274A CN 201480079936 A CN201480079936 A CN 201480079936A CN 106460274 A CN106460274 A CN 106460274A
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- Prior art keywords
- fiber mat
- fiber
- fibre
- unidirectional
- mat
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Links
- 239000000835 fiber Substances 0.000 title claims abstract description 340
- 238000000034 method Methods 0.000 title claims abstract description 57
- 230000002787 reinforcement Effects 0.000 title claims abstract description 15
- 238000004519 manufacturing process Methods 0.000 claims abstract description 39
- 239000002131 composite material Substances 0.000 claims abstract description 24
- 229920005989 resin Polymers 0.000 claims abstract description 22
- 239000011347 resin Substances 0.000 claims abstract description 22
- 230000008569 process Effects 0.000 claims abstract description 10
- 238000001802 infusion Methods 0.000 claims abstract description 8
- 238000010276 construction Methods 0.000 claims description 22
- 230000007704 transition Effects 0.000 claims description 14
- 239000011230 binding agent Substances 0.000 claims description 9
- 239000000843 powder Substances 0.000 claims description 9
- 230000003014 reinforcing effect Effects 0.000 claims description 8
- 239000004744 fabric Substances 0.000 claims description 7
- 239000000853 adhesive Substances 0.000 claims description 4
- 230000001070 adhesive effect Effects 0.000 claims description 4
- 238000009960 carding Methods 0.000 claims description 2
- 239000010410 layer Substances 0.000 description 60
- 239000000463 material Substances 0.000 description 20
- 239000011521 glass Substances 0.000 description 19
- 238000013461 design Methods 0.000 description 8
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 7
- 238000005429 filling process Methods 0.000 description 7
- 229920000642 polymer Polymers 0.000 description 7
- 238000009745 resin transfer moulding Methods 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 239000007788 liquid Substances 0.000 description 5
- 239000000047 product Substances 0.000 description 5
- 239000011162 core material Substances 0.000 description 4
- 239000003365 glass fiber Substances 0.000 description 4
- 230000010412 perfusion Effects 0.000 description 4
- 238000005452 bending Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 238000009826 distribution Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000003822 epoxy resin Substances 0.000 description 3
- 239000011151 fibre-reinforced plastic Substances 0.000 description 3
- 239000002657 fibrous material Substances 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 229920000647 polyepoxide Polymers 0.000 description 3
- 229920000728 polyester Polymers 0.000 description 3
- 229920001567 vinyl ester resin Polymers 0.000 description 3
- 125000000391 vinyl group Chemical group [H]C([*])=C([H])[H] 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000004814 polyurethane Substances 0.000 description 2
- 239000002356 single layer Substances 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 241000538562 Banjos Species 0.000 description 1
- HECLRDQVFMWTQS-UHFFFAOYSA-N Dicyclopentadiene Chemical compound C1C2C3CC=CC3C1C=C2 HECLRDQVFMWTQS-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000000227 grinding Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000013067 intermediate product Substances 0.000 description 1
- 239000003562 lightweight material Substances 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 230000037452 priming Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 230000037303 wrinkles Effects 0.000 description 1
Classifications
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04H—MAKING TEXTILE FABRICS, e.g. FROM FIBRES OR FILAMENTARY MATERIAL; FABRICS MADE BY SUCH PROCESSES OR APPARATUS, e.g. FELTS, NON-WOVEN FABRICS; COTTON-WOOL; WADDING ; NON-WOVEN FABRICS FROM STAPLE FIBRES, FILAMENTS OR YARNS, BONDED WITH AT LEAST ONE WEB-LIKE MATERIAL DURING THEIR CONSOLIDATION
- D04H3/00—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length
- D04H3/02—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments
- D04H3/04—Non-woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of forming fleeces or layers, e.g. reorientation of yarns or filaments in rectilinear paths, e.g. crossing at right angles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
- B29C65/481—Non-reactive adhesives, e.g. physically hardening adhesives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/72—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by combined operations or combined techniques, e.g. welding and stitching
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/304—In-plane lamination by juxtaposing or interleaving of plies, e.g. scarf joining
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
- F03D1/0675—Rotors characterised by their construction elements of the blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2313/00—Use of textile products or fabrics as reinforcement
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2220/00—Application
- F05B2220/30—Application in turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/20—Manufacture essentially without removing material
- F05B2230/23—Manufacture essentially without removing material by permanently joining parts together
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/60—Assembly methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/21—Rotors for wind turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2280/00—Materials; Properties thereof
- F05B2280/60—Properties or characteristics given to material by treatment or manufacturing
- F05B2280/6003—Composites; e.g. fibre-reinforced
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Textile Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
- Nonwoven Fabrics (AREA)
- Reinforced Plastic Materials (AREA)
Abstract
A method of producing a single assembled longitudinally extending fibre layer for use in a later resin infusion process for manufacturing a fibre-reinforced composite structure is described. The method includes the steps of: a) providing a first fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the first fibre mat between two ends, b) providing a second fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the second fibre mat between two ends, c) arranging the first fibre mat and the second fibre mat so that unidirectional fibres of one end of the first fibre mat adjoin one end of the second fibre mat in a single plane at a common boundary, and d) splicing unidirectional fibres of the first fibre mat at said one end of the first fibre mat to unidirectional fibres of the second fibre mat at said one end of the second fibre mat in order to form a splicing joint.
Description
Technical field
The present invention relates to a kind of fibrolaminar method of longitudinal extension manufacturing single assembling, this fibrous layer is in follow-up manufacture
Use in the resin infusion technique of fiber reinforcement composite construction.The invention additionally relates to a kind of by least one this assembling
The method that fibrous layer manufactures wind turbine blade part.The invention still further relates to a kind of fiber of longitudinal extension of assembling is strengthened
Layer, this fabric reinforcement uses in follow-up manufacturing in the resin infusion technique that composite construction strengthened by fiber.
Background technology
Wind turbine blade to manufacture generally according to one of two kinds of structure designs, that is, thin aerodynamic housing
It is glued to the design on spar, or spar caps（Also referred to as main laminate）It is integrated in setting in aerodynamic housing
Meter.
In the first design, spar constitutes the bearing structure of blade.Spar and aerodynamic housing or housing section
Divide and be fabricated separately.Aerodynamic housing is typically made into two housing parts, generally Pressure side shell part and suction
Enter side body part.This two housing parts are glued or are otherwise coupled to spar and the leading edge along housing parts
Cementing each other further with trailing edge.This design has the advantage that, that is,：Crucial bearing structure can be separately made, and
And therefore be easier to control.In addition, this design allows to use various different manufacture methods（Such as molding and silk wind work processed
Skill）To manufacture beam.
In second design, spar caps or main laminate be integrated in housing and with aerodynamic casing moulds
Together.Main laminate generally comprises the fibrous layer of comparatively high amts compared with the remainder of blade, and can form wind-force
It is such at least for fibrolaminar quantitative aspects that the local of turbine cylinder thickeies.Therefore, main laminate is permissible
Form the fibre insertion in blade.In this type of design, main laminate constitutes bearing structure.Blade shell is generally designed with
Be integrated in Pressure side shell partly in the first main laminate and the second main laminate of being integrated in the housing parts of suction side.The
One main laminate and the second main laminate are typically connected by one or more shear web, and described shear web may, for example, be
C-shaped or I shape.For very long blade, blade shell further includes positioned at pressure along at least a portion of longitudinal extension part
The first additional main laminate in power side body and the second additional main laminate being located in suction side body.These add
Main laminate can also be connected by one or more shear web.This design has the advantage that：More easily by leaf
The molding of piece housing parts is controlling the aerodynamic shape of blade.
Priming by vacuum or vacuum assisted resin transfer moulding（VARTM）It is typically used for manufacturing composite construction, for example include
A kind of method of the wind turbine blade of fiber-reinforced matrix material.
During filling mould, vacuum is produced by the vacuum outlet in die cavity（Here described vacuum is understood
For insufficient pressure or negative pressure）, it is inhaled in die cavity to fill described die cavity via access road by this liquid polymers.When above
Polymer flow towards vacuum passage mobile when, due to negative pressure, polymer is dispersed in die cavity in all directions from access road.
It is therefore important that optimally positioning access road and vacuum passage, to obtain being filled up completely with of die cavity.But it is it is ensured that poly-
Distribution completely in whole die cavity for the compound is typically difficult, therefore this frequently result in so-called do, that is, have and do not set
The region of the fibrous material of fat fully perfusion.Therefore, doing is such region, that is,：In this region, fibrous material is not filled
Note, and there may be by controlling vacuum pressure and being difficult to eliminate or can not possibly eliminate in the possible superpressure of entrance side
Air pocket.In the vacuum injection technology of the rigid die part using vacuum bag form and resilient mould part, can be in filling
By piercing through vacuum bag and by for example right with syringe needle extraction air in corresponding position after the operation of mould
Do and place under repair.Alternatively, liquid polymerses can be injected in corresponding position, and this can also for example pass through syringe needle
Carry out.This is a time-consuming and loaded down with trivial details process.In the case of large mold part, staff must stand in vacuum bag
On.This is undesirable, particularly when polymer does not also harden, because this may lead to the change of the fibrous material of insertion
Shape, and therefore lead to the local weakness of structure, consequently, it is possible to leading to such as curvature effect.
Resin transfer moulding（RTM）It is a kind of manufacture method similar to VARTM.In RTM, due to producing in die cavity
Vacuum, liquid resin is not drawn in die cavity.Alternatively, liquid resin is forced into die cavity by the overvoltage of entrance side
In.
In most of the cases, the polymer applied or resin be polyester, vinyl esters or epoxy resin but it is also possible to
It is polyurethane（PUR）Or poly- bicyclopentadiene（pDCPD）, and fiber reinforcement is typically based on glass fibre or carbon fiber.Epoxy
Resin has the advantage that in various aspect of performances, contraction for example during curing（May result in some cases in layered product relatively
Few fold）, electrical characteristic and machinery and fatigue strength aspect.Polyester and vinyl esters this have the advantage that them to gel
Coating provides more preferable bond propertiess.Thus, before arranging in a mold fiber reinforced materials, by gel coat is applied
Use mould, gel coat can be administered to the outer surface of housing during the manufacture of housing.It can thus be avoided various moulds
Operate after system, for example, blade is coated.Additionally, polyester and vinyl esters are more cheap than epoxy resin.Therefore, it can simplify system
Make technique, and can be with reduces cost.
Generally, composite construction includes being covered with fiber reinforced materials, for example one or more fiber-reinforced polymer layers
Core material.Core material can serve as sept between these layers to form sandwich, and generally by rigid lightweight material
Material is made to reduce the weight of composite construction.In order to ensure the efficient distribution of liquid resin in dipping process, core material is permissible
It is provided with resin distribution network, for example, realized by setting passage or groove in the surface of core material.
Become increasing in time course with the blade being for example used for wind turbine, and can exceed that now
70 meters long, and the amount of fiber reinforced materials also increases.When manufacturing the blade with spar caps, including the fiber mat quilt of unidirectional fibre
It is laid in multiple layers of the whole length along main laminate, to provide rigidity for main laminate.Fiber mat is generally from coiled material
Apply and be cut to Len req.Many glass fiber reinforcement blades use H- glass（H-glass）.Although allowing to comprise layer
Piece successively decreases（ply drops）Synusia joint be used for E- glass（E-glass）, but this synusia joint is not allowed for H- glass
Glass, because the joint of overlap leads to unacceptable fold and therefore reduces intensity.This actually means that if fiber mat volume
Material is terminated with the length shorter than main laminate, then this end piece must be dropped and start new coiled material.For example, if for
47.6 meters of blade, H glass volume terminates at apart from 25 meters of root, then 25 meters of H glass will have to discard.The excess causing
The waste of fiber reinforced materials be significant.
However, even for E- glass, being likely to bring problem from the use of the end piece of fiber mat coiled material, because grinding
Study carefully and have shown that internal synusia lap 32% in overlapping intensity decreases.Additionally, often observing in this lap
To fold.This fold leads to the change of rigidity in wind turbine blade and mechanical weakness.
Content of the invention
It is an object of the invention to provide a kind of new method of the part for manufacturing wind turbine blade and intermediate products,
It overcomes or improves at least one shortcoming of prior art or provides useful replacement scheme.
According in a first aspect, the invention provides a kind of manufacture single assembling the fibrolaminar method of longitudinal extension, this fibre
Dimension layer uses in follow-up manufacturing in the resin infusion technique that composite construction strengthened by fiber, the method comprising the steps of：
a）There is provided the first fiber mat, the first fiber mat includes the list orienting between the ends on the longitudinal direction of the first fiber mat
To reinforcing fibre,
b）There is provided the second fiber mat, the second fiber mat includes the list orienting between the ends on the longitudinal direction of the second fiber mat
To reinforcing fibre,
c）Arrange the first fiber mat and the second fiber mat so that the unidirectional fibre of one end of the first fiber mat is at public boundary
One end of adjacent second fiber mat in single plane,
d）The unidirectional fibre of the first fiber mat of the described end of the first fiber mat is spliced to described the one of the second fiber mat
The unidirectional fibre of the second fiber mat at end, to form joints.
This provides ratio in final composite construction and passed through two or more non-splicing fiber mats before filling process
The higher laminate layer of conventional laminate layer manufacturing.Furthermore, it is possible to the quantity of the fold in minimizing layered product, thus more enter one
Step reduces the mechanical weakness in final composite construction.This is especially due to joints ensure that two pads during process of deployment
（For example when additional fibrous layer is arranged in the fibrolaminar top of assembling, or when fiber reinforced materials are subsequently by vacuum holding
When bag and perfusion）Do not move and be achieved.
Additionally, the advantage of the method is, the excessive fiber reinforcement pad being for example derived from coiled material can be used for being formed finally
Monolayer in composite construction and do not damage the mechanical strength of composite construction.This may be special for the H- glass being generally not allowed joint
Not useful.This significantly reduces to discard and measure and reduce manufacturing cost.
Fiber mat is dry fibers pad, i.e. untreated fiber mat.Thus, it will be seen that the present invention relates to including multiple lists
The manufacture of the single fabric reinforcement of only fiber mat, and this single fabric reinforcement impregnated with resin after the fabrication,
Resin is subsequently hardened or is cured to form composite construction.
The splicing of fiber mat can be carried out in mould, carries out during the laying of single longitudinal layer, or can be
It is held on and carries out on the platform on mould, or can carry out outside mould, be made up of excess fibre pad with being for example used for being formed
New fiber reinforced materials volume.The splicing of fiber mat can be used for manufacturing the fiber synusia with length-specific.By choosing
Select for example suitable excess fibre pad, the position of joint can also be controlled.Can cut or prune the end of the fiber mat of splicing
Portion, to produce the synusia of length-specific.
Hereinafter, unidirectional fibre will be abbreviated as UD fiber sometimes.
Mean that, before resin infusion process after a while, the UD fiber of the first fiber mat is pre- according to the splicing of the present invention
First bond or be otherwise affixed to the UD fiber of the second fiber mat.
Filling process may, for example, be resin transfer moulding（RTM）Or vacuum assisted resin transfer moulding（VARTM）.
Obviously, the first fiber mat and the second fiber mat all include first end and the second end.Therefore, the second of the first fiber mat
End can be assembled with the first end of the second fiber mat.It should be appreciated that this process can continue so that the second fiber mat second
End can be assembled with the first end of the 3rd fiber mat further, etc..Therefore, the fibrous layer of assembling can be included containing splicing
Multiple joints of UD fiber.
The UD of the UD fiber in the described end of the first fiber mat and the described end in described second fiber mat is fine
Dimension is preferably arranged so that they overlap each other in longitudinal region in a longitudinal direction.This overlap can be in every way
There is provided.According to preferred implementation, first fibrolaminar described one end and second fibrolaminar described one end are conically cut,
Wherein step c）In described fibrous layer be arranged so that the fibrolaminar longitudinal direction of the longitudinal extension in single assembling for the public boundary
Side is upwardly formed the tapering transition between the unidirectional fibre of the first fiber mat and the unidirectional fibre of the second fiber mat.This embodiment
Provide big splicing boundary and overlap, thus providing the especially strong preliminary splicing between two fiber mats.
Tapering transition advantageously has 1：50 to 1：Thickness between 5-length ratio, for example, about 1：30.
In one embodiment, binding agent or viscosifier are used for providing described splicing.It should be noted, however, that binding agent
Only with a certain amount of use of UD fiber fixing at public boundary, and should not form can not ooze infringement later stage filling process
Region thoroughly.
Binding agent is preferably powder base.Powder based adhesive may, for example, be Neoxil powder.Such embodiment party
Formula has shown that can provide very favorable joints, without damaging the profit of fiber in subsequent filling process
Wet.
In another embodiment, joints are heated, for example, pass through flatiron heated.This can promote two fibres
Green tack between dimension pad combines, for example, carried out by melting powder based adhesive；Additionally, flatiron can provide fiber mat
Between frictional engagement.Binding agent combines only to provide and tentatively combines effect, and not with infringement group in follow-up filling process
The amount of the fibrolaminar moistening of dress provides.
In another embodiment, step d）It is stitched together including by the first fiber mat and the second fiber mat to provide
The step of described splicing.Therefore, it can provide between the UD fiber of two pads and be mechanically connected, without in follow-up perfusion
During damage fiber moistening.
Suture and binding agent splicing can be used together or be used alone.
According to an embodiment, can arrange thin further along the public boundary of the first fiber mat and the second fiber mat
Yarn（scrim）, such as glass tape or a chopped strand pad（chopped strand mat）.Tulle can suture or adhere to
Two fiber mats, to improve the splicing between fiber.Tulle can for example be attached at the surface of assembled layers, such as upper surface.Thin
Yarn may, for example, be glass tape or chopped strand pad.
In another embodiment, the unidirectional fibre of the first fiber mat is pressed against the unidirectional fibre of the second fiber mat, so that
Form frictional connection between described unidirectional fibre.Therefore, fiber can contact with each other and provide frictional engagement or entanglement, with
Further splicing is provided between fiber.Frictional engagement can be carried out before staples pad.
In another embodiment, step d）Including using roller by the unidirectional fibre of the first pad and second fiber mat
Unidirectional fibre presses to each other.In one embodiment, the horizontal direction of the fiber mat along assembling for the roller rolls, that is, along joints
Roll.However, in another embodiment, roller rolls along the longitudinal direction.The width of roller can correspond to the first fiber mat and
The width of the second fiber mat.
Roller can advantageously comprise the first roller and the second roller, such as upper roller and lower roll.Roller can be arranged to have corresponding to
The interval of the thickness of fiber mat.One of roller can have the surface of corrugated or fluting；When rolling in a longitudinal direction,
This surface may be used to UD alignment of fibers.The width of ripple can correspond to the width of the fibre bundle of the UD fiber including fiber mat
Degree.Roller can be hollow or tubulose.Additionally, roller can be provided with opening or hole in roller surface.Therefore, it can apply to roller
Plus air pressure or suction.For example, it is possible to apply air pressure and to another roller applying suction to a roller.This can pass through
Form the loose fiber bundle being connected to each other to promote the frictional engagement between two UD fibers padding.Suction can advantageously apply
To the roller with corrugated surface or grooved surface, so that it is guaranteed that fiber enters in groove and when roller rolls along the longitudinal direction pair
Together.
In one embodiment, the first fiber mat and the second fiber are cut in the direction in a direction substantially perpendicular to longitudinal direction
Respective described one end of pad.In another embodiment, respective described one end of the first fiber mat and the second fiber mat
Angled up in the side being substantially perpendicular to longitudinal direction.This angle for example can form the sharp of 30 to 85 degree with longitudinal direction
Angle.Described one end can also be with zigzag pattern-cut on the horizontal direction of the first fiber mat and the second fiber mat.
In an advantageous embodiment, in step d）Before, described the one of the first fiber mat and the second fiber mat
Unidirectional fibre at end is disengaged suture at the longitudinal region of described end.With regard to this point it is noted that UD fiber mat leads to
Often suture in a lateral direction, such as to form fibre bundle.However, it will of course be appreciated that the UD fiber mat for non-suture can
To realize identical effect.Then, untie the unidirectional fibre of suture preferably overlapping to form public boundary, and subsequently each other
Engage, be preferably so that two fibrous layers in step d）Suture is untied in above-mentioned longitudinal overlap region before.
Obviously, UD fiber is in step d）Differ afterwards and be shaped as tapered edges circle, particularly have been provided between the fibers
In the case of frictional connection.
In one embodiment, described one end of the first fiber mat and the second fiber mat described end unidirectional
Fiber passes through such as carding apparatus（comb）Etc alignment means align in a longitudinal direction.This make two fiber mats it
Between the fold that often occurs of boundary minimize and provide firm suture to combine.Therefore, any mechanical weakness is also
Minimize in whole composite construction.
The UD fiber of fiber mat is preferably E- glass, H- glass or carbon fiber.
According to second aspect, the invention provides a kind of manufacture wind turbine blade part（Such as blade shell member）
Method, wherein this manufacture method includes laying in a mold fibrous layer, and wherein at least one fibrous layer is according in said method
Any one manufacturing, and wherein subsequently resin is supplied to described fibrous layer and is subsequently cured or hardens to form composite junction
Structure.Composite construction can for example be manufactured by RTM or VARTM process.
Therefore, the invention provides a kind of manufacture the wind turbine blade part being made up of fiber reinforced polymer material
Method, described fiber reinforced polymer material includes polymeric matrix and embedded fiber armature in the polymer matrix
Material, wherein said method comprises the following steps：
i）The shaped structure including die cavity and having longitudinal direction is provided,
ii）The fibrous layer of the multiple stackings extending is placed along along the longitudinal direction of shaped structure,
iii）In step ii）There is provided resin in mold cavity afterwards, and
iv）It is cured or hardened resin to form composite construction, wherein
At least one of fibrous layer of the plurality of stacking is the assembling fibrous layer being manufactured according to said method.
The fibrous layer of the plurality of stacking preferably includes UD fiber.Mould preferably has the negative shape of final composite construction
Shape（negative shape）Mould.Fibrous layer is advantageously along the longitudinal direction arrangement of mould.Therefore, also edge is vertical for unidirectional fibre
To arrangement.
In one embodiment, laying is related to multiple fibrolaminar stackings, and at least one fibrous layer wherein said
It is clipped in and do not have between two fibrous layers of joints at the fibrolaminar joints of at least one assembling described.This two
Fibrous layer is preferably also UD fiber mat.
Thus, it will be seen that the method is related to normally lay program, wherein advantageously, continuous layer is arranged in mould
In, and only using the layer of the fiber mat including splicing, to reduce the amount of reject product.
In one embodiment, wind turbine blade part is bearing structure, such as main laminate or spar caps.Main
Layered product or spar caps can be integrated in blade shell member, or it can be manufactured to single part.
According to the third aspect, the invention provides a kind of assembling, longitudinal extension fiber according to said method manufacture
Enhancement layer.Therefore, the invention provides a kind of assembling, longitudinal extension fabric reinforcement, it adds in follow-up manufacture fiber
Use in the resin infusion technique of strong composite construction, this fabric reinforcement includes：
- the first fiber mat, it is included on the longitudinal direction of the first fiber mat at two ends（First end and the second end）Between orient
Unidirectional reinforcing fibre,
- the second fiber mat, it is included on the longitudinal direction of the second fiber mat at two ends（First end and the second end）Between orient
Unidirectional reinforcing fibre, wherein
- the first fiber mat and the second fiber mat are arranged so that the unidirectional fibre of one end of the first fiber mat at public boundary
Single plane in adjacent second fiber mat one end, and wherein
The unidirectional fibre of the first fiber mat of the described end of the-the first fiber mat is spliced to described one end of the second fiber mat
The unidirectional fibre of second fiber mat at place, and form joints.
Brief description
Shown embodiment explains in detail the present invention with reference to the accompanying drawings, in the accompanying drawings：
Fig. 1 shows wind turbine；
Fig. 2 is the perspective schematic view of the wind turbine blade according to the present invention；
Fig. 3 shows the fibrolaminar perspective schematic view of main laminate；
Fig. 4 is fibrolaminar schematic longitudinal view of main laminate；
Fig. 5 is the fibrolaminar schematic side elevation of the assembling according to the present invention；
Fig. 6 is the first fibrolaminar schematic plan of assembling according to the present invention；
Fig. 7 is the second fibrolaminar schematic plan of assembling according to the present invention；
Fig. 8 is the 3rd fibrolaminar schematic plan of assembling according to the present invention；
Fig. 9 is the 4th fibrolaminar schematic plan of assembling according to the present invention；
Figure 10 is the 5th fibrolaminar schematic plan of assembling according to the present invention；
Figure 11 is the 6th fibrolaminar schematic plan of assembling according to the present invention；
Figure 12 is the 7th fibrolaminar schematic side elevation of assembling according to the present invention；
Figure 13 is the flow chart of the example illustrating to manufacture the fibrolaminar step of assembling according to the present invention；
Figure 14 shows the schematic diagram of the roller for the present invention；And
Figure 15 shows the schematic side elevation of roller.
Specific embodiment
Fig. 1 shows the modern windward type wind turbine 2 of the routine according to so-called " Denmark's concept ", and it has tower portion
4th, fuselage 6 and the rotor with approximate horizontal armature spindle.Rotor includes hub portion 8 and three blades radially extending from hub portion 8
10, each blade 10 has the root of blade 16 near hub portion and the vane tip 14 farthest away from hub portion 8.Rotor has uses R
The radius representing.
Fig. 2 shows the schematic diagram of the first embodiment of the wind turbine blade 10 according to the present invention.Wind turbine
Machine blade 10 has the shape of traditional wind turbine blade, and includes：Root area 30 near hub portion；Farthest away from
The type face in hub portion or airfoil area 34；And it is located at the transitional region 32 between root area 30 and airfoil area 34.Blade 10
Including leading edge 18 and trailing edge 20, when blade is arranged in hub portion, leading edge 18 is towards the direction of rotation of blade 10, and trailing edge 20
Rightabout towards leading edge 18.
Airfoil area 34（Also referred to as type face region）There is the leaf of ideal in terms of the generation of lift or near ideal
Plate shape, and root area 30 then has circular or oval cross section due to structural considerations, for example, make it possible to
Enough blade 10 is easier and is safely attached to hub portion.The diameter of root area 30（Or string）Can be along whole root area
Domain 30 is constant.Transitional region 32 has the airfoil profile in circle from root area 30 or elliptical shape airfoil region 34
The transition profile gradually changing.The chord length of transitional region 32 typically increases with increasing apart from r away from hub portion.Airfoil area 34
There is airfoil profile, this airfoil profile has the string extending between the leading edge 18 of blade 10 and trailing edge 20.The width of string with
Increase apart from r away from hub portion and reduce.
The shoulder 40 of blade 10 is defined to the position that blade 10 has its largest chord strong point.Shoulder 40 is generally located on transition
Boundary between region 32 and airfoil area 34.
It should be noted that the string of the different sections of blade is not generally located in common plane because blade may reverse and/
Or bending（That is, pre-bending）, thus provide have correspondingly reverse and/or bending circuit string plane, this be most commonly that for
The local velocity compensating blade depends on the situation of the radius away from hub portion.
Blade is generally made up of Pressure side shell part 36 and suction side shell part 38, Pressure side shell part 36 and inhale
Power side body part 38 is glued each other along the joint line at the leading edge 18 of blade and trailing edge 20.
Hereinafter, the present invention is explained in the manufacture with regard to Pressure side shell part 36 or suction side shell part 38.
As shown in figure 3, suction side shell part 38 includes spar caps or main laminate 50, main laminate 50 substantially along
The whole length of suction side shell part 38 extends on the longitudinal direction of suction side shell part.Main laminate 50 includes multiple
Fibrous layer or pad 52, fibrous layer or pad 52 include unidirectional fibre（UD fiber）, it is typically more than 20 fibrous layers.Fiber mat is usual
Apply from the coiled material of dry type and be cut to required length.Then fiber laying is carried out vacuum bagged and irrigates resin,
Resin is finally cured to form composite construction.Many glass fiber reinforcement blades use H- glass.Although allowing to comprise synusia
The synusia joint successively decreasing is used for E- glass, but this synusia joint is not allowed for H- glass.This actually mean that if
Fiber mat coiled material is terminated with the length shorter than main laminate, then this extremity piece will must be dropped and start new coiled material.For example,
If for 47.6 meters of blade, H glass coiled material is terminating at 25 meters of root, then 25 meters of H glass will have to discard.
The waste of the fiber reinforced materials of the excess causing is significant.
The present invention as shown in Figure 4 passes through to manufacture assembling fibrous layer 52 ' to solve this problem, this conjugate fiber layer 52 '
Including at least first fiber mat 54 and the second fiber mat 55, wherein UD fiber the end of two fiber mats 54,55 splice with
Form assembling fibrous layer 52 '.Two fiber mats 54,55 are arranged in single plane does not have synusia to pass so that assembled layers 52 ' are formed
The monolayer subtracting.This provides ratio in final composite construction and passed through two or more non-splicing fiber mats before filling process
The higher laminate layer of conventional laminate layer manufacturing.Furthermore, it is possible to the quantity of the fold in minimizing layered product, thus more enter one
Step reduces the mechanical weakness in final composite construction.This is especially due to joints ensure that two pads during process of deployment
（For example when additional fibrous layer is arranged in the fibrolaminar top of assembling, or when fiber reinforced materials are subsequently by vacuum holding
When bag and perfusion）Do not move and be achieved.It can be seen from figure 4 that the fibrous layer 52 ' of assembling or at least assembling region are clipped in
Between two continuous fiber layers 52 that the splicing regions of the fibrous layer 52 ' of assembling are not spliced.
Preferred implementation according to Fig. 5, the UD fiber of the UD fiber of the first fiber mat 54 and the second fiber mat 55
By taper-cut so that the UD fiber of two fiber mats 54,55 is adjacent to each other at public boundary 56, this results in two pads
54th, the tapering transition between 55 UD fiber.The UD fiber of two fiber mats passes through preliminary connection（For example pass through binding agent, seam
Close or frictional connection）And splice each other.The fibrous layer 52 ' of assembling is overall to be provided with dry type, that is, be not impregnated with, and it is essential that
Splice or tentatively connect without compromising on resin infusion process after a while.Therefore, preliminary connection is only established as guaranteeing that UD fiber does not wrinkle
Pleat, and two fiber mats 54,55 do not move during laying or follow-up vacuum bagging and filling process.In order to provide relatively
Seamlessly transitting between long public boundary 56 and the UD fiber of two fiber mats 54,55, the ratio of thickness and length is 1：50 to
1：Between 5, advantageously 1：30 about.
Fig. 6 shows the top view of the first embodiment of the assembled layers 52 ' according to the present invention.UD fiber is perpendicular to group
The longitudinal direction cutting of dress layer 52 ', and the taper so that between the UD fiber of two pads 54,55 is conically cut in end
Transition is formed on the longitudinal direction of assembled layers.
Fig. 7 shows the top view of the second embodiment of the assembled layers according to the present invention, the wherein first fiber mat 154
UD fiber and the UD fibre splices of the second fiber mat 155.UD fiber be cut so that end face with assembling fiber mat horizontal side
Angled to comparing.This angle for example can become about 10 degree with horizontal direction, or be equal to and become 80 degree with longitudinal direction.End
Portion is cut further so that the tapering transition between the UD fiber of two pads 154,155 is in the fibrolaminar longitudinal direction side of assembling
It is upwardly formed.
Fig. 8 shows the top view of the 3rd embodiment of the assembled layers according to the present invention, the wherein first fiber mat 254
UD fiber and the UD fibre splices of the second fiber mat 255.UD fiber is cut into so that end is towards horizontal direction, the word of formation
Shape pattern.End is cut further so that the tapering transition between the UD fiber of two pads 254,255 is in the fibrous layer assembling
Longitudinal direction on formed.
It should be mentioned that various embodiments can be combined for cutting angle.For example, it is possible to by having along inclining
The zigzag pattern at oblique angle and the combination of the embodiment shown in Fig. 7 and Fig. 8 is provided.This embodiment can be by any possibility
Little change profile on the longer fore-and-aft distance of fiber mat.
Fig. 9 shows the top view of the 4th embodiment of the assembled layers according to the present invention, the wherein first fiber mat 354
UD fiber and the UD fibre splices of the second fiber mat 355.The UD of the UD fiber of the first fiber mat 354 and the second fiber mat 355 is fine
Dimension is illustrated conically to cut so that the UD fiber of two fiber mats 354,355 is adjacent to each other at public boundary, and this is in longitudinal direction
Tapering transition between the UD fiber of two pads 354,355 is defined on direction.In this embodiment, closed by double slit
360 come to promote splice.
Figure 10 shows the top view of the 5th embodiment of the assembled layers according to the present invention, the wherein first fiber mat 454
UD fiber and the second fiber mat 455 UD fibre splices.The UD fiber of the first fiber mat 454 and the UD of the second fiber mat 455
Fiber is illustrated conically to cut so that the UD fiber of two fiber mats 454,455 is adjacent to each other at public boundary, and this is vertical
Tapering transition between the UD fiber of two pads 454,455 is defined on direction.In this embodiment, by single seam
Zygonema 460 promotes splicing.
Figure 11 shows the top view of the 6th embodiment of the assembled layers according to the present invention, the wherein first fiber mat 554
UD fiber and the second fiber mat 555 UD fibre splices.The UD fiber of the first fiber mat 554 and the UD of the second fiber mat 555
Fiber is illustrated conically to cut so that the UD fiber of two fiber mats 554,555 is adjacent to each other at public boundary, and this is vertical
Tapering transition between the UD fiber of two pads 554,555 is defined on direction.In this embodiment, by a zigzag
Suture 560 promotes splicing.
Although these embodiments are shown to have the preferred implementation of tapering transition betwixt, it should be noted that
Arrive, public boundary must be not necessarily taper.However, the UD fiber of usual two pads should be overlapping in a longitudinal direction, make
Obtain and can realize splicing.
Moreover, it will be appreciated that the sewing method shown in Fig. 9 to Figure 11 can be combined, for example, pass through to suture zigzag
To realize with single suture or the charge-coupled conjunction of double slit.
However, it is also possible to by the banjo fixing butt jointing shape border between the UD fiber of two fiber mats as shown in figure 12 Lai real
The splicing of existing fiber.In this embodiment, the UD fiber of the first fiber mat 654 passes through tulle 670 and the second fiber mat 655
UD fibre splices.This tulle may, for example, be glass tape or chopped strand pad.Tulle can pass through suture, frictional connection, bonding
The combination of agent or these modes is connected to two fiber mats.
Figure 13 shows that the manufacture according to the present invention assembles an example of the step involved by fibrous layer 752 '.First
In step 700, including in transverse direction suture 784 UD fibre bundle 774 the first fiber mat 754 in the first fiber mat 754
Suture is untied in end regions.The longitudinal extent untiing the region of suture can be of about for example 10cm.In second step 710
In, the end of the first fibrous layer 754 is conically cut.In third step, UD fiber is combed and aligns, so that it is guaranteed that fine
Dimension bundle extends in a longitudinal direction.
In four steps 730, including the UD fibre bundle 775 of suture 785 in transverse direction the second fiber mat 755 the
Suture is untied in the end regions of two fiber mats 755.The longitudinal extent untiing the region of suture can be of about for example 10cm.?
In 5th step 740, the end of the second fibrous layer 755 is conically cut.In the 6th step, UD fiber is combed and right
Together, so that it is guaranteed that fibre bundle extends in a longitudinal direction.
In the 7th step 760, Neoxil powder 788 is applied to the UD fibre untiing suture of the first fiber mat 754
Dimension.Then, the second fiber mat 755 is arranged so that the UD fiber untiing suture of the second fiber mat 755 in the 8th step 770
With the first fiber mat 754 untie suture UD fiber overlapping.In the 9th step 780, the overlapping UD fiber of suture will be untied
Heating and flatiron are so that Neoxil powder melts and provides the splicing between the UD fiber of two pads 754,755, and are formed
The fibrous layer 752 ' of assembling.
Although being shown as by being spliced using binder powders according to the fibrolaminar manufacture method of assembling of the present invention,
But it would be recognized that splicing step can also be held by the combination of other binding agents, suture, frictional connection or these modes
OK.
Figure 14 shows front schematic view, and Figure 15 shows the schematic side elevation of roller system, and this roller system can be used for
Frictional connection between the UD fiber of the first fiber mat 854 and the UD fiber of the second fiber mat 855 is provided.Roller system includes first
Roller 890 and the second roller 895.First roller 890 has the corrugated surface with multiple spines 891.First roller is hollow, and
Surface includes multiple holes 892.Second roller is also hollow, and includes multiple holes 896 on surface.Roller system allows to
Forced air is applied to the entrance 897 of the second roller and applies suction 893 to the inside of the hollow of the first roller.By the second roller
The air discharge in 895 hole 896 produces loose fibre bundle to the UD fiber untiing suture, and is guaranteed by the suction in hole 892
Fibre bundle aligns in the spine 891 of the first roller 890.Thickness according to fiber mat 854,85 5 sets between two rollers 890
Distance.The width of spine 891 of the first roller 890 and depth set according to desired UD fiber bundle cross-section size.Roller 890 He
895 roll in a longitudinal direction along the UD fiber of two fiber mats 854,85 5, and can roll around the scheduled time or
Until realizing sufficient frictional connection.
Describe the present invention by reference to Advantageous embodiments.However, the scope of the present invention is not limited to shown embodiment party
Formula, and can be changed and modified in the case of without departing from the scope of the present invention.
Reference numerals list
| 2 | Wind turbine |
| 4 | Tower portion |
| 6 | Fuselage |
| 8 | Hub portion |
| 10 | Blade |
| 14 | Vane tip |
| 16 | Root of blade |
| 18 | Leading edge |
| 20 | Trailing edge |
| 30 | Root area |
| 32 | Transitional region |
| 34 | Airfoil area |
| 36 | Pressure side shell part |
| 38 | Suction side shell part |
| 40 | Shoulder |
| 50 | Spar caps/main laminate |
| 52 | Fibrous layer |
| 52’ | The fibrous layer of assembling |
| 54、154、254、354、454、554、654、754、854 | First fiber mat |
| 55、155、255、355、455、555、655、755、855 | Second fiber mat |
| 56 | Public boundary |
| 360、460、560 | Suture |
| 670 | Tulle |
| 700、710、720、730、740、750、760、770、780 | Step |
| 774、775 | Unidirectional fibre |
| 784、785 | Suture |
| 788 | Powder adhesives |
| 890 | First roller |
| 891 | Spine |
| 892 | Hole |
| 893 | Suction |
| 895 | Second roller |
| 896 | Hole |
| 897 | Entrance |
| R | Local radius, away from the radial distance of root of blade |
| L | Length of blade |
Claims (15)
1. a kind of fibrolaminar method of the longitudinal extension manufacturing single assembling, described fibrous layer is strengthened in follow-up manufacture fiber
Use in the resin infusion technique of composite construction, the method comprising the steps of：
a）There is provided the first fiber mat, described first fiber mat is included on the longitudinal direction of described first fiber mat between the ends
The unidirectional reinforcing fibre of orientation,
b）There is provided the second fiber mat, described second fiber mat is included on the longitudinal direction of described second fiber mat between the ends
The unidirectional reinforcing fibre of orientation,
c）Arrange described first fiber mat and described second fiber mat so that the unidirectional fibre of one end of described first fiber mat exists
One end of described second fiber mat is adjoined in single plane at public boundary,
d）The unidirectional fibre of described first fiber mat of the described end of described first fiber mat is spliced to described second fine
The unidirectional fibre of described second fiber mat of described end of dimension pad, to form joints.
2. method according to claim 1, wherein, described first fibrolaminar described one end and described second fibrolaminar
Described one end is conically cut, wherein step c）In described fibrous layer be arranged so that described public boundary single continuous
The fibrolaminar longitudinal direction of longitudinal extension on form the unidirectional fibre of described first fiber mat and described second fiber mat
Tapering transition between unidirectional fibre.
3. method according to claim 2, wherein, described tapering transition has 1：50 to 1：Thickness-length between 5
Ratio e.g., from about 1：30 thickness-length ratio.
4. according to method in any one of the preceding claims wherein, wherein, step d）Described including being provided using binding agent
Splicing.
5. method according to claim 4, wherein, described adhesive is powder base.
6. according to method in any one of the preceding claims wherein, wherein, described joints are heated, for example, pass through flatiron
Heated.
7. according to method in any one of the preceding claims wherein, wherein, step d）Including by described first fiber mat and institute
State the step that the second fiber mat is stitched together to provide described splicing.
8. according to method in any one of the preceding claims wherein, wherein, the unidirectional fibre of described first fiber mat is pressed against institute
State the unidirectional fibre of the second fiber mat, to form frictional connection between described unidirectional fibre.
9. according to method in any one of the preceding claims wherein, wherein, step d）Including using roller, described first is padded
Unidirectional fibre and the unidirectional fibre of described second fiber mat be pressed against each other.
10. according to method in any one of the preceding claims wherein, wherein, in step d）Before, in described first fiber mat
Described end and described second fiber mat described end unidirectional fibre at the longitudinal region of described end quilt
Untie suture.
11. according to method in any one of the preceding claims wherein, wherein, in described one end and the institute of described first fiber mat
State the unidirectional fibre of described end of the second fiber mat by the alignment means of such as carding apparatus etc in a longitudinal direction
Alignment.
A kind of 12. manufacture wind turbine blade parts, the method for such as blade shell member, wherein this manufacture method includes
Fibrous layer is laid, wherein at least one fibrous layer passes through any one in the method according to claim 1 to 11 in mould
Method is manufacturing, and wherein subsequently resin is supplied to described fibrous layer and is subsequently cured or hardens to form composite construction.
13. methods manufacturing wind turbine blade part according to claim 12, wherein, described laying is related to multiple
Fibrolaminar stacking, and at least one fibrous layer wherein said is clipped in and do not have at least one fibrolaminar joints described
Have between two fibrous layers of joints.
The method of the 14. manufacture wind turbine blade parts according to claim 12 or 13, wherein, described wind turbine
Machine blade part is bearing structure, such as main laminate or spar caps.
A kind of 15. assemblings, the fabric reinforcement of longitudinal extension, for manufacturing, in follow-up, the resin that composite construction strengthened by fiber
Use in instillation process, described fabric reinforcement includes：
- the first fiber mat, described first fiber mat includes orienting between the ends on the longitudinal direction of described first fiber mat
Unidirectional reinforcing fibre,
- the second fiber mat, described second fiber mat includes orienting between the ends on the longitudinal direction of described second fiber mat
Unidirectional reinforcing fibre, wherein
- described first fiber mat and described second fiber mat are arranged so that the unidirectional fibre of one end of described first fiber mat
One end of described second fiber mat is adjoined in the single plane at public boundary, and wherein
The unidirectional fibre of described first fiber mat of the described end of-described first fiber mat is spliced to described second fiber
The unidirectional fibre of described second fiber mat of described end of pad, and form joints.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/EP2014/062526 WO2015192867A1 (en) | 2014-06-16 | 2014-06-16 | A method of producing a continuous fibre reinforcement layer from individual fibre mats |
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| Publication Number | Publication Date |
|---|---|
| CN106460274A true CN106460274A (en) | 2017-02-22 |
| CN106460274B CN106460274B (en) | 2019-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201480079936.6A Active CN106460274B (en) | 2014-06-16 | 2014-06-16 | By the method for individual fiber mat manufacture continuous fiber enhancement layer |
Country Status (10)
| Country | Link |
|---|---|
| US (1) | US10513810B2 (en) |
| EP (1) | EP3155159B1 (en) |
| CN (1) | CN106460274B (en) |
| BR (1) | BR112016029528B1 (en) |
| CA (1) | CA2951738C (en) |
| DK (1) | DK3155159T3 (en) |
| ES (1) | ES2676269T3 (en) |
| PL (1) | PL3155159T3 (en) |
| TR (1) | TR201808856T4 (en) |
| WO (1) | WO2015192867A1 (en) |
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| CN109098929A (en) * | 2017-06-21 | 2018-12-28 | 通用电气公司 | The associated method of wind turbine blade and manufacture with hybrid spar caps |
| CN110345001A (en) * | 2018-04-05 | 2019-10-18 | 西门子歌美飒可再生能源公司 | Pultruded fiber composite strip with tapered width and thickness ends for wind turbine spar caps |
| CN111716865A (en) * | 2017-06-29 | 2020-09-29 | 发那科株式会社 | Method for manufacturing resin composite board |
| CN113306236A (en) * | 2021-07-12 | 2021-08-27 | 重庆泛锐科技有限公司 | High-strength composite board and preparation method thereof |
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| EP3099477B1 (en) * | 2014-01-31 | 2020-12-23 | LM WP Patent Holding A/S | Wind turbine blade with improved fibre transition |
| US9869295B2 (en) * | 2015-05-07 | 2018-01-16 | General Electric Company | Attachment method to install components, such as tip extensions and winglets, to a wind turbine blade, as well as the wind turbine blade and component |
| US9869296B2 (en) * | 2015-05-07 | 2018-01-16 | General Electric Company | Attachment method and system to install components, such as tip extensions and winglets, to a wind turbine blade |
| GB201700913D0 (en) * | 2017-01-19 | 2017-03-08 | Univ Leuven Kath | Continuous prepregs for natural fibre-reinforced composites |
| US11572861B2 (en) * | 2017-01-31 | 2023-02-07 | General Electric Company | Method for forming a rotor blade for a wind turbine |
| DE102018100941A1 (en) * | 2018-01-17 | 2019-07-18 | Wobben Properties Gmbh | Method for producing components of a wind energy plant, in particular of a wind turbine rotor blade |
| DK180532B1 (en) | 2019-04-23 | 2021-06-10 | Envision Energy Denmark Aps | A WIND WINDOW WING AND A METHOD FOR MANUFACTURING THE WIND WIND WING |
| WO2022212829A1 (en) * | 2021-04-02 | 2022-10-06 | Lm Wind Power A/S | Systems and methods for manufacturing rotor blades |
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- 2014-06-16 US US15/318,398 patent/US10513810B2/en active Active
- 2014-06-16 BR BR112016029528-5A patent/BR112016029528B1/en active IP Right Grant
- 2014-06-16 CN CN201480079936.6A patent/CN106460274B/en active Active
- 2014-06-16 PL PL14730881T patent/PL3155159T3/en unknown
- 2014-06-16 ES ES14730881.1T patent/ES2676269T3/en active Active
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- 2014-06-16 CA CA2951738A patent/CA2951738C/en active Active
- 2014-06-16 EP EP14730881.1A patent/EP3155159B1/en active Active
- 2014-06-16 DK DK14730881.1T patent/DK3155159T3/en active
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| US6627024B2 (en) * | 2002-01-07 | 2003-09-30 | Owens Corning Fiberglas Technology, Inc. | Method and apparatus for splicing fibrous mats |
| CN101918197A (en) * | 2007-09-04 | 2010-12-15 | Lm玻璃纤维制品有限公司 | A method of producing a composite structure via intermediate products, the related apparatus and a composite structure obtainable by the method |
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| CN109098929A (en) * | 2017-06-21 | 2018-12-28 | 通用电气公司 | The associated method of wind turbine blade and manufacture with hybrid spar caps |
| CN111716865A (en) * | 2017-06-29 | 2020-09-29 | 发那科株式会社 | Method for manufacturing resin composite board |
| CN110345001A (en) * | 2018-04-05 | 2019-10-18 | 西门子歌美飒可再生能源公司 | Pultruded fiber composite strip with tapered width and thickness ends for wind turbine spar caps |
| CN110345001B (en) * | 2018-04-05 | 2021-06-11 | 西门子歌美飒可再生能源公司 | Pultruded fiber composite strip with tapered width and thickness ends for wind turbine spar caps |
| CN113306236A (en) * | 2021-07-12 | 2021-08-27 | 重庆泛锐科技有限公司 | High-strength composite board and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| EP3155159A1 (en) | 2017-04-19 |
| BR112016029528B1 (en) | 2021-11-03 |
| CA2951738C (en) | 2021-08-03 |
| US10513810B2 (en) | 2019-12-24 |
| PL3155159T3 (en) | 2018-10-31 |
| CN106460274B (en) | 2019-02-01 |
| WO2015192867A1 (en) | 2015-12-23 |
| BR112016029528A2 (en) | 2017-08-22 |
| US20170121877A1 (en) | 2017-05-04 |
| DK3155159T3 (en) | 2018-07-16 |
| CA2951738A1 (en) | 2015-12-23 |
| TR201808856T4 (en) | 2018-07-23 |
| EP3155159B1 (en) | 2018-04-04 |
| ES2676269T3 (en) | 2018-07-18 |
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